CN106547965A - A kind of temperature barrier of hypersonic gliding class aircraft - Google Patents
A kind of temperature barrier of hypersonic gliding class aircraft Download PDFInfo
- Publication number
- CN106547965A CN106547965A CN201610929527.1A CN201610929527A CN106547965A CN 106547965 A CN106547965 A CN 106547965A CN 201610929527 A CN201610929527 A CN 201610929527A CN 106547965 A CN106547965 A CN 106547965A
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- China
- Prior art keywords
- heat shield
- heat
- temperature barrier
- bearing layer
- thermal insulation
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/28—Fuselage, exterior or interior
Abstract
The invention discloses a kind of temperature barrier of hypersonic gliding class aircraft, which includes heat shield, thermal insulation layer and bearing layer, thermal insulation layer is covered on bearing layer, heat shield is covered on thermal insulation layer, heat shield mutually separates with the bearing layer and without connection physically or contact, to ensure heat shield and the bearing layer Free Transform under Aerodynamic Heating environment, heat shield includes polylith, polylith heat shield mutually splices to form entirety, corner of the polylith heat shield in bay section, the corner portion of bay section, mutually splice the junction of horizontal tail and nacelle, multiple solar heat protection bars are partially provided with the heat shield and load interlayer of bay section joint, multiple solar heat protection bar separated by gap, solar heat protection bar can be slidably with respect to heat shield, to adapt to stress deformation, solar heat protection bar is identical with the heat shield material.The present invention by the separate design of heat shield block design, heat shield and bearing layer, can effectively solving is thermally matched and a thermal stress difficult problem, improve the reliability of temperature barrier.
Description
Technical field
The invention belongs to superb ski-running Xiang class aircraft thermal protection technology field, is related to a kind of new reliable separation formula heat anti-
Protection structure, for hypersonic gliding class aircraft thermal protection, can be thermally matched in effectively solving thermal protection conceptual design and hot answers
A power difficult problem, improves the reliability of thermal protection system design.
Background technology
Hypersonic gliding class aircraft (referring generally to flight speed more than Ma5), as flight Mach number is high, typically adopts
Complex lift body or blended wing-body aerodynamic configuration, and glide maneuver flight of jumping, with stronger mobility and prominent
Anti- ability, has huge military value and potential economic worth, it has also become weapon and spacecraft development both at home and abroad at present
Main way.
In low latitude dense atmosphere flight, aircraft faces more harsh Aerodynamic Heating to the gliding class aircraft, flight
Device typical parts heat flow density peak value reaches 1.8MW/m2, and total heating amount is 60MJ/m2.Due to being melted using lift body or wing body
Fit aerodynamic configuration, more harsh compared with the pneumatic thermal environment of the local location of tipping, aircraft surface heat flow density gradient is larger.One
Aspect, the heat flow density of larger gradient cause the thermograde of heat insulation material larger, cause heat insulation material to have larger thermal stress；
On the other hand, the harsh Aerodynamic Heating of long-time causes the larger thermal deformation of different structure part, thermally matched difficulty larger.Such as,
In the typical bay section of 500mm × 600mm × 500mm, using conventional heat protection design structure, local thermal stress reaches
150MPa, the safe handling beyond material require that deflection reaches 2mm, is unsatisfactory for total technical index.
To ensure hypersonic gliding class aircraft flight work, need to be improved thermal protection structure design, to drop
Low complex appearance, thermal protection system pressure under severe pneumatic thermal environment.
Therefore, reasonable is feasible, economical and efficient, cleverly thermal protection structure is hypersonic gliding class aircraft for design
Thermal protection system key issue to be solved.
The content of the invention
Disadvantages described above and Improvement requirement shortcoming for prior art, present invention aim at a kind of hypersonic gliding class
The temperature barrier of aircraft, which passes through heat shield carries out the separate design of block design, heat shield and bearing layer, effectively can solve
Certainly thermally matched in a thermal protection conceptual design and thermal stress difficult problem, improves the reliability of thermal protection system design.
For achieving the above object, the present invention provides a kind of temperature barrier of hypersonic gliding class aircraft, and which includes
Heat shield, thermal insulation layer and bearing layer, wherein,
The thermal insulation layer is covered on bearing layer, and the heat shield is covered on thermal insulation layer,
The heat shield mutually separates with the bearing layer and without connection physically or contact, to ensure the heat shield
With the bearing layer under Aerodynamic Heating environment Free Transform,
The heat shield includes polylith, and polylith heat shield mutually splices to form entirety, and described in polylith, heat shield is in bay section
Corner, the corner portion of bay section, the junction of horizontal tail and nacelle mutually splice,
Multiple solar heat protection bars are partially provided with the heat shield and load interlayer of bay section joint, multiple solar heat protection bars are separated by
Gap, the solar heat protection bar with respect to heat shield can slidably, to adapt to stress deformation,
The solar heat protection bar is identical with the heat shield material.
Further, the heat shield is ceramic heat insulation material, the tensile strength of its ceramic heat insulation material be 80Mpa～
120Mpa。
Further, the edge portion per heat shield described in block is provided with step surface, with by overlapping and fixing step surface
And realize the splicing between heat shield block.
Further, the step surface of overlapping is fixed with screw, the material of the screw is identical with the heat shield, the spiral shell
Follow closely as sunk screw.
Further, the thickness of the heat shield is 6mm～8mm, and the thickness of the step surface is 3mm～4mm.
Further, the heat conductivity of the thermal insulation layer is less than 0.1W/mk, and the density of the thermal insulation layer is 200kg/m3~
300kg/m3。
In general, following beneficial effect can be obtained by the contemplated above technical scheme of the present invention：
Under the conditions of harsher and circumferential larger gradient Aerodynamic Heating, the block design of heat shield can effectively reduce solar heat protection
Layer normal direction and circumferential thermal stress, it is to avoid destruction of the stress concentration of heat shield local to heat shield.Between heat shield and bearing layer
Separate, under Time Aero-Heating environment, heat shield and load interlayer can Free Transforms.A kind of new thermal protection of the present invention
Structure, can thermally matched in an effectively solving thermal protection conceptual design and thermal stress difficult problem, improve the reliability of thermal protection system design
Property.
Description of the drawings
Fig. 1 is the structural representation of the novel separated type temperature barrier according to the embodiment of the present invention；
Fig. 2 is the cross-sectional view of the novel separated type temperature barrier according to the embodiment of the present invention；
In all of the figs, identical reference represents same feature, specifically：
1- bearing layers, 2- attachment screws, 3- thermal insulation layers, 4- heat shields, 5- screw holes.
Specific embodiment
In order that the objects, technical solutions and advantages of the present invention become more apparent, it is below in conjunction with drawings and Examples, right
The present invention is further elaborated.It should be appreciated that specific embodiment described herein is only to explain the present invention, and
It is not used in the restriction present invention.As long as additionally, technical characteristic involved in invention described below each embodiment
Do not constitute conflict each other can just be mutually combined.
The present invention provides a kind of reliable separation formula temperature barrier, for hypersonic gliding class aircraft thermal protection, prevents
Thermosphere adopts piecemeal molding, connects into bay section by each piece by screw, and screw material is with heat insulation material parent, heat shield, heat-insulated
It is separated from each other between layer and bearing layer.Under the pneumatic thermal environment of harsher compared with Aerodynamic Heating and circumferential larger gradient, heat shield point
Block design can effectively reduce heat shield normal direction and circumferential thermal stress, it is to avoid the stress concentration of heat shield local is broken to heat shield
It is bad.Separate between heat shield and bearing layer, under Time Aero-Heating environment, heat shield and load interlayer can Free Transforms.
Apparatus of the present invention can thermally matched in an effectively solving thermal protection conceptual design and thermal stress difficult problem, improve thermal protection system design
Reliability.
Fig. 1 is the structural representation of the novel separated type temperature barrier according to the embodiment of the present invention；Fig. 2 is according to this
The cross-sectional view of the novel separated type temperature barrier of bright embodiment, two figures from more than, the new reliable separation formula
Temperature barrier includes heat shield, thermal insulation layer and bearing layer, and thermal insulation layer is covered on bearing layer, and heat shield is covered in thermal insulation layer
On, bearing layer can be metal material, alternatively sandwich, be such as the resin base of carbon fiber or glass fiber reinforcement
Composite, thermal insulation layer are lightweight, the metal of porous or non-metal honeycomb material, and heat shield is the ceramic base with some strength
Thermally protective materials.Heat shield, thermal insulation layer, bearing layer and attachment screw together form the temperature barrier of complex appearance.
More specifically, the heat shield mutually separates with the bearing layer and without connection physically or contact, to ensure
The heat shield and the bearing layer Free Transform under Aerodynamic Heating environment, the heat shield include polylith, polylith heat shield
Mutually splicing to form entirety, friendship of the heat shield described in polylith in the corner of bay section, the corner portion of bay section, horizontal tail and nacelle
Meet place mutually to splice.In Practical Project, at the stress raiser of bay section and the demoulding difficulty in molding heat shield
Heat shield piecemeal can be connected, the largest benefit of piecemeal connection is alleviation stress concentration.
Multiple solar heat protection bars are partially provided with the heat shield and load interlayer of bay section joint, multiple solar heat protection bars are separated by
Gap, the solar heat protection bar can slidably, to adapt to stress deformation with respect to heat shield.When there is stress concentration, solar heat protection bar can be with
Deformation is absorbed, equally plays a part of to alleviate stress concentration.Solar heat protection bar is identical with the heat shield material, and the heat shield is pottery
Porcelain heat insulation material, the tensile strength of its ceramic heat insulation material is 80Mpa～120Mpa.
In one embodiment of the invention, the edge portion per heat shield described in block is provided with step surface, with by folded
Merge fixed step surface and realize the splicing between heat shield block.With screw fix overlapping step surface, the material of the screw with
The heat shield is identical, and the screw is sunk screw.The thickness of the heat shield be 6mm～8mm, the thickness of the step surface
For 3mm～4mm.
In another embodiment of the present invention, the heat conductivity of the thermal insulation layer is less than 0.1W/mk, the thermal insulation layer it is close
Spend for 200kg/m3～300kg/m3.The advantage for so limiting is to take into account weight and heat-proof quality simultaneously.
In Practical Project, hypersonic gliding class aircraft adopts lift body or blended wing-body aerodynamic configuration, compared with
The pneumatic thermal environment of local location of tipping is more harsh, and aircraft surface heat flow density gradient is larger.On the one hand, larger gradient
Heat flow density causes the thermograde of heat insulation material larger, causes heat insulation material to have larger thermal stress；On the other hand, long-time
Harsh Aerodynamic Heating causes the larger thermal deformation of different structure part, and thermally matched difficulty is larger.
For above practical problem, in the present invention, heat shield adopts piecemeal molding, connects into cabin by each piece by screw
Section, screw material are separated from each other between heat shield, thermal insulation layer and bearing layer with heat insulation material parent.It is harsher and it is circumferential compared with
During big gradient Aerodynamic Heating, the block design of heat shield, it is possible to decrease molding heat shield technology difficulty and production cost, can have
Effect reduces heat shield normal direction and circumferential thermal stress, it is to avoid destruction of the stress concentration of heat shield local to heat shield.Heat shield and
Separate between bearing layer, under Time Aero-Heating environment, heat shield and load interlayer can Free Transforms.
The present invention is explained in more detail below by by embodiment, but following examples are merely illustrative, especially
It is the explanation just in terms of stand-alone device in the concrete size and cabin etc., protection scope of the present invention receives these embodiments
Restriction.
In the present embodiment, flight time of below aircraft 50km is 400s, bay section size be 500mm × 600mm ×
500mm complicated D type bay sections, solar heat protection thickness are 8mm, and insulation thickness is 12mm, and bearing layer thickness is 2.5mm.Front deck solar heat protection
Layer is divided into upper and lower two parts, is attached with the screw of 16 M6, by aeroheating analysis, bay section line outer wall peak temperature windward
For 1500 DEG C, 1700 DEG C of incline outer wall peak temperature, 800 DEG C of crosswind line outer wall peak temperature, incline is to crosswind line thermograde
Larger, using separate type thermal protection scheme, heat insulation material thermal stress is reduced to below 100Mpa, and thermal deformation, can be with below 1mm
Meet use requirement.
As it will be easily appreciated by one skilled in the art that the foregoing is only presently preferred embodiments of the present invention, not to
The present invention, all any modification, equivalent and improvement made within the spirit and principles in the present invention etc. are limited, all should be included
Within protection scope of the present invention.
Claims (6)
1. it is a kind of it is hypersonic gliding class aircraft temperature barrier, it is characterised in which includes heat shield, thermal insulation layer and holds
Power layer, wherein,
The thermal insulation layer is covered on bearing layer, and the heat shield is covered on thermal insulation layer,
The heat shield mutually separates with the bearing layer and without connection physically or contact, to ensure the heat shield and institute
Bearing layer Free Transform under Aerodynamic Heating environment is stated,
The heat shield includes polylith, and polylith heat shield mutually splices to form entirety, heat shield turning in bay section described in polylith
At angle, the junction of the corner portion of bay section, horizontal tail and nacelle mutually splice,
Multiple solar heat protection bars, multiple solar heat protection bar phase compartments are partially provided with the heat shield and load interlayer of bay section joint
Gap, the solar heat protection bar with respect to heat shield can slidably, to adapt to stress deformation,
The solar heat protection bar is identical with the heat shield material.
2. the temperature barrier of a kind of hypersonic gliding class aircraft as claimed in claim 1, it is characterised in that described anti-
Thermosphere is ceramic heat insulation material, and the tensile strength of its ceramic heat insulation material is 80Mpa～120Mpa.
3. a kind of temperature barrier of hypersonic gliding class aircraft as claimed in claim 2, it is characterised in that the institute per block
The edge portion for stating heat shield is provided with step surface, to realize the splicing between heat shield block by overlapping and fixing step surface.
4. the temperature barrier of a kind of hypersonic gliding class aircraft as claimed in claim 3, it is characterised in that with screw
The step surface of fixed overlapping, the material of the screw are identical with the heat shield, and the screw is sunk screw.
5. as described in one of claim 1-4 it is a kind of hypersonic gliding class aircraft temperature barrier, it is characterised in that
The thickness of the heat shield is 6mm～8mm, and the thickness of the step surface is 3mm～4mm.
6. the temperature barrier of a kind of hypersonic gliding class aircraft as claimed in claim 5, it is characterised in that it is described every
The heat conductivity of thermosphere is less than 0.1W/mk, and the density of the thermal insulation layer is 200kg/m3～300kg/m3。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610929527.1A CN106547965A (en) | 2016-10-31 | 2016-10-31 | A kind of temperature barrier of hypersonic gliding class aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610929527.1A CN106547965A (en) | 2016-10-31 | 2016-10-31 | A kind of temperature barrier of hypersonic gliding class aircraft |
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| CN106547965A true CN106547965A (en) | 2017-03-29 |
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| CN201610929527.1A Pending CN106547965A (en) | 2016-10-31 | 2016-10-31 | A kind of temperature barrier of hypersonic gliding class aircraft |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108225711A (en) * | 2017-12-15 | 2018-06-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of thermally protective materials antiscour test bracket |
| CN110723275A (en) * | 2019-10-24 | 2020-01-24 | 湖北航天技术研究院总体设计所 | High-temperature heat-proof opening cover structure |
| CN110901885A (en) * | 2019-12-23 | 2020-03-24 | 湖北航天技术研究院总体设计所 | Thermal protection system of aircraft |
| CN111114750A (en) * | 2019-12-20 | 2020-05-08 | 山东工业陶瓷研究设计院有限公司 | Thermal protection device and reentry vehicle |
| CN112009666A (en) * | 2020-09-08 | 2020-12-01 | 四川航天***工程研究所 | Heat insulation protection device of gliding aircraft |
| CN113021226A (en) * | 2021-03-03 | 2021-06-25 | 航天特种材料及工艺技术研究所 | Sleeving tool and sleeving method for upper closed type outer heat-proof layer of cabin section |
| CN113466894A (en) * | 2021-06-09 | 2021-10-01 | 航天恒星科技有限公司 | Protection system of emergency positioning transmitter |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108225711A (en) * | 2017-12-15 | 2018-06-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of thermally protective materials antiscour test bracket |
| CN110723275A (en) * | 2019-10-24 | 2020-01-24 | 湖北航天技术研究院总体设计所 | High-temperature heat-proof opening cover structure |
| CN111114750A (en) * | 2019-12-20 | 2020-05-08 | 山东工业陶瓷研究设计院有限公司 | Thermal protection device and reentry vehicle |
| CN110901885A (en) * | 2019-12-23 | 2020-03-24 | 湖北航天技术研究院总体设计所 | Thermal protection system of aircraft |
| CN110901885B (en) * | 2019-12-23 | 2021-11-30 | 湖北航天技术研究院总体设计所 | Thermal protection system of aircraft |
| CN112009666A (en) * | 2020-09-08 | 2020-12-01 | 四川航天***工程研究所 | Heat insulation protection device of gliding aircraft |
| CN112009666B (en) * | 2020-09-08 | 2021-10-08 | 四川航天***工程研究所 | Heat insulation protection device of gliding aircraft |
| CN113021226A (en) * | 2021-03-03 | 2021-06-25 | 航天特种材料及工艺技术研究所 | Sleeving tool and sleeving method for upper closed type outer heat-proof layer of cabin section |
| CN113466894A (en) * | 2021-06-09 | 2021-10-01 | 航天恒星科技有限公司 | Protection system of emergency positioning transmitter |
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Application publication date: 20170329 |